A satellite with a primary imaging mirror fabricated while in space is described. The primary mirror is formed by solidifying liquid precursor material which assumes a paraboloid shape upon certain rotational maneuvers of the satellite. The primary mirror is preferably formed from a molten metal which creates a rigid paraboloid primary mirror upon solidification. The mirror material can be pre-melted prior to launch and carried to orbit while liquid, or it can be stored as a solid and melted in space to create the mirror.

A solar array wing includes an extension mast to be extended from a wound state, and a support member, around which the extension mast is wound, to support the extension mast after the extension mast is extended. The support member is made of a fiber reinforced composite material. A coefficient of linear expansion of the fiber reinforced composite material, a unit of which is for each degree Celsius, in a direction that is orthogonal to an extension direction of the extension mast, is higher than or equal to −1×10.sup.−6 and lower than or equal to 1×10.sup.−6.

A retractable mast solar array includes a collapsible boom extensible by a boom deployer. At least one foldable upper arm assembly is coupled to the collapsible boom. At least one foldable lower arm assembly coupled to the collapsible boom. A foldable solar array includes two or more columns of blanket elements, each column of blanket elements is affixed at one end to the at least one foldable upper arm assembly and at an opposite end to the at least one foldable lower arm assembly. In a stowed state, the two or more columns of blanket elements are stowed folded in either or both of the at least one foldable upper arm assembly or the at least one foldable lower arm assembly, and in a deployed state, the two or more columns of blanket elements are unfolded to a deployed solar array.

A transportation network for providing propellant in space can include optical mining vehicles that concentrate solar energy to spall captured asteroids, capture released volatiles, and store them in reservoirs as propellants. The network can also have orbital transfer vehicles that use solar thermal rocket modules that focus solar energy on heat exchangers to force propellant through nozzles, as well as separable aeromaneuvering tanker modules with reusable heatshields and storage tanks. The network can have propellant depots positioned between Earth and a transport destination. The depots can mechanically couple to accept propellant delivery and to supply it to visiting space vehicles.

A transportation network for providing propellant in space can include optical mining vehicles that concentrate solar energy to spall captured asteroids, capture released volatiles, and store them in reservoirs as propellants. The network can also have orbital transfer vehicles that use solar thermal rocket modules that focus solar energy on heat exchangers to force propellant through nozzles, as well as separable aeromaneuvering tanker modules with reusable heatshields and storage tanks. The network can have propellant depots positioned between Earth and a transport destination. The depots can mechanically couple to accept propellant delivery and to supply it to visiting space vehicles.

A release mechanism for releasably securing a releasable structure to a stationary structure, where the mechanism employs release balls that can re-secure the releasable structure to the stationary structure. The release mechanism includes a base portion having three rails extending radially outward from a center of the base portion, and a rotatable portion rotatably mounted to the base portion, where the rotatable portion has a cam indentation. The release balls are positioned between the base portion and the rotatable portion so that one of the release balls is ridable on each of the rails and all of the release balls are positioned within the cam indentation. The cam indentation is configured so that as the rotatable portion is rotated relative to the base portion the cam indentation causes and allows the release balls to move along the rails in unison with each other to hold and release the releasable structure.

A device for mounting a load to a carrier is described. The device includes a first support configured for fixation to the carrier; a second support configured for fixation to the load. The first and second supports are spaced away from each other viewed along a main load bearing axis of the device. The device further includes an outer shell extending along the main load bearing axis, and an inner member that is within the outer shell. The device includes a damping material connecting the inner member to at least the outer shell, wherein one of the outer shell and the inner member connects the first support and the second support to each other.

A multilayer sealed skin, in particular for an inflatable structure and that includes a first polymer film, a reinforcing fabric disposed on the first polymer film and a second polymer film disposed on the reinforcing fabric and adhered by means of an adhesive to the first polymer film through cavities in the reinforcing fabric. The skin can be applied to the production of an inflatable structural element such as an inflatable beam for which the skin forms an outer wall of the structural element and for which the first film of the skin forms an inner face of the outer wall of the structural element, and the second film forms an outer face of the wall.

A computer system of the present invention comprises a processor unit, and is configured to be capable of communicating with a user device operated by a first user and a satellite. The satellite includes a religious object and an information providing means for providing information associated with the religious object. The processor unit is configured to execute at least the following: acquiring location data indicating a location on Earth of the first user; acquiring bearing data indicating a bearing; calculating, on the basis of the location data and the bearing data, a time period in which the satellite is located in a predetermined space extending toward the bearing from the location on Earth of the first user; and providing the user device with information associated with the religious object provided by the information providing means of the satellite only during the time period.

A computer system of the present invention comprises a processor unit, and is configured to be capable of communicating with a user device operated by a first user and a satellite. The satellite includes a religious object and an information providing means for providing information associated with the religious object. The processor unit is configured to execute at least the following: acquiring location data indicating a location on Earth of the first user; acquiring bearing data indicating a bearing; calculating, on the basis of the location data and the bearing data, a time period in which the satellite is located in a predetermined space extending toward the bearing from the location on Earth of the first user; and providing the user device with information associated with the religious object provided by the information providing means of the satellite only during the time period.